EP3446983B1 - Système de vide pour système de dégazage de carburant - Google Patents

Système de vide pour système de dégazage de carburant Download PDF

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Publication number
EP3446983B1
EP3446983B1 EP18189736.4A EP18189736A EP3446983B1 EP 3446983 B1 EP3446983 B1 EP 3446983B1 EP 18189736 A EP18189736 A EP 18189736A EP 3446983 B1 EP3446983 B1 EP 3446983B1
Authority
EP
European Patent Office
Prior art keywords
chamber
fuel
housing
movable assembly
assembly
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP18189736.4A
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German (de)
English (en)
Other versions
EP3446983A1 (fr
Inventor
Gerald P. Dyer
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Hamilton Sundstrand Corp
Original Assignee
Hamilton Sundstrand Corp
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Filing date
Publication date
Application filed by Hamilton Sundstrand Corp filed Critical Hamilton Sundstrand Corp
Publication of EP3446983A1 publication Critical patent/EP3446983A1/fr
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01D—SEPARATION
    • B01D19/00—Degasification of liquids
    • B01D19/0036—Flash degasification
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01D—SEPARATION
    • B01D19/00—Degasification of liquids
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01D—SEPARATION
    • B01D19/00—Degasification of liquids
    • B01D19/0031—Degasification of liquids by filtration
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01D—SEPARATION
    • B01D19/00—Degasification of liquids
    • B01D19/0063—Regulation, control including valves and floats
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D37/00—Arrangements in connection with fuel supply for power plant
    • B64D37/005—Accessories not provided for in the groups B64D37/02 - B64D37/28
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D37/00—Arrangements in connection with fuel supply for power plant
    • B64D37/34—Conditioning fuel, e.g. heating
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04B—POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS
    • F04B23/00—Pumping installations or systems
    • F04B23/04—Combinations of two or more pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04B—POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS
    • F04B25/00—Multi-stage pumps
    • F04B25/02—Multi-stage pumps of stepped piston type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04B—POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS
    • F04B35/00—Piston pumps specially adapted for elastic fluids and characterised by the driving means to their working members, or by combination with, or adaptation to, specific driving engines or motors, not otherwise provided for
    • F04B35/008—Piston pumps specially adapted for elastic fluids and characterised by the driving means to their working members, or by combination with, or adaptation to, specific driving engines or motors, not otherwise provided for the means being a fluid transmission link
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04B—POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS
    • F04B39/00—Component parts, details, or accessories, of pumps or pumping systems specially adapted for elastic fluids, not otherwise provided for in, or of interest apart from, groups F04B25/00 - F04B37/00
    • F04B39/0005—Component parts, details, or accessories, of pumps or pumping systems specially adapted for elastic fluids, not otherwise provided for in, or of interest apart from, groups F04B25/00 - F04B37/00 adaptations of pistons
    • F04B39/0016—Component parts, details, or accessories, of pumps or pumping systems specially adapted for elastic fluids, not otherwise provided for in, or of interest apart from, groups F04B25/00 - F04B37/00 adaptations of pistons with valve arranged in the piston
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04B—POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS
    • F04B53/00—Component parts, details or accessories not provided for in, or of interest apart from, groups F04B1/00 - F04B23/00 or F04B39/00 - F04B47/00
    • F04B53/06—Venting
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01D—SEPARATION
    • B01D19/00—Degasification of liquids
    • B01D19/0068—General arrangements, e.g. flowsheets
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01D—SEPARATION
    • B01D2257/00—Components to be removed
    • B01D2257/10—Single element gases other than halogens
    • B01D2257/104—Oxygen
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01D—SEPARATION
    • B01D35/00—Filtering devices having features not specifically covered by groups B01D24/00 - B01D33/00, or for applications not specifically covered by groups B01D24/00 - B01D33/00; Auxiliary devices for filtration; Filter housing constructions
    • B01D35/005—Filters specially adapted for use in internal-combustion engine lubrication or fuel systems
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01D—SEPARATION
    • B01D35/00—Filtering devices having features not specifically covered by groups B01D24/00 - B01D33/00, or for applications not specifically covered by groups B01D24/00 - B01D33/00; Auxiliary devices for filtration; Filter housing constructions
    • B01D35/30—Filter housing constructions
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01D—SEPARATION
    • B01D63/00—Apparatus in general for separation processes using semi-permeable membranes
    • B01D63/005—Microfluidic devices
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Definitions

  • This invention generally relates to fuel systems, and more particularly, to stabilization of fuel via deoxygenation systems.
  • Aircraft fuel is often utilized as a coolant for various aircraft systems.
  • the presence of dissolved oxygen in aircraft fuel may be objectionable because the oxygen supports oxidation reactions that may yield undesirable by-products.
  • aerated fuel is heated above 121.1°C (250°F)
  • the oxygen contained therein initiates free radical reactions resulting in deposits commonly referred to as "coke” or "coking.”
  • Coke may be detrimental to the fuel lines and may inhibit combustion. The formation of such deposits may impair the normal functioning of a fuel system, either with respect to an intended heat exchange function or the efficient injection of fuel.
  • US 2013/343934 A1 relates to a vacuum assembly and US 7569099 B2 relates to a fuel system.
  • a vacuum assembly according to claim 1 is provided.
  • the energy conversion device 12 includes a gas turbine engine, such as commonly used in vehicle including but not limited to a fixed or rotary wing aircraft for example.
  • the fuel configured to power the energy conversion device 12 may additionally serve as a coolant for one or more subsystems of the vehicle and becomes heated as it is delivered to the fuel injectors immediately prior to combustion.
  • the fuel system 10 includes a deoxygenator system 14 that receives a liquid fuel F from a reservoir 16, for example a fuel tank.
  • the fuel F is typically a hydrocarbon, such as aircraft fuel for example.
  • the energy conversion device 12 may exist in a variety of forms in which the fuel, at some point prior to eventual use for processing, such as combustion or some form of energy release, acquires sufficient heat to support autoxidation reactions and coking if dissolved oxygen is present in the fuel to any significant extent.
  • a heat exchange system 18 represents a system through which the fuel passes in a heat exchange relationship. It should be understood that the heat exchange section 18 may be directly associated with the energy conversion device 12 and/or distributed elsewhere in the larger fuel system 10. The heat exchange system 18 may alternatively or additionally include a plurality of heat exchanges distributed throughout the system 10.
  • fuel F stored in the reservoir 16 normally contains dissolved oxygen, such as at a saturation level of 70 ppm for example. However, it should be understood that a fuel having any level of dissolved oxygen is contemplated herein.
  • a fuel pump 20 draws the fuel F from the reservoir 16.
  • the fuel pump 20 communicates with the reservoir 16 via a fuel reservoir conduit 22 and a valve 24 to a fuel inlet 26 of the deoxygenator system 14.
  • the pressure applied by the fuel pump 20 assists in circulating the fuel F through the deoxygenator system 14 and other portions of the fuel system 10.
  • oxygen is selectively removed into a vacuum system 28.
  • the deoxygenated fuel F d flows from a fuel outlet 30 of the deoxygenation system 14 via a deoxygenated fuel conduit 32, to the heat exchange system 18 and to the ECD 12 such as the fuel injectors of a gas turbine engine.
  • a portion of the deoxygenated fuel F d may be recirculated, as represented by recirculation conduit 34 to either the deoxygenation system 14 and/or the reservoir 16.
  • the deoxygenator system 14 includes a multiplicity of gas/fuel micro-channel assemblies 36.
  • the assemblies 36 include a composite oxygen permeable membrane (not shown) between a fuel channel (not shown) and an oxygen receiving vacuum assembly 40 which permits the flow of nitrogen and/or another oxygen-free gas ( FIG. 3 ).
  • the channels may be of various shapes and arrangements to provide a pressure differential, which maintains an oxygen concentration differential across the membrane to deoxygenate the fuel.
  • the composite oxygen permeable membrane preferably includes oxygen permeable membranes, which allow dissolved oxygen (and other gases) to diffuse through angstrom-size voids but exclude the larger fuel molecules, and permeable membranes which use a solution-diffusion mechanism to dissolve the oxygen (and/or other gases) and allow it (or them) to diffuse through the membrane, while excluding the fuel.
  • the vacuum assembly 40 includes an enclosure or housing 42 having a generally hollow interior within which a movable assembly 44 is located.
  • an o-ring or other suitable device 50 extends between the first portion 46 of the movable assembly 44 and the housing 42 to form a seal preventing the flow of a fluid there between.
  • a first chamber 52 is defined within the housing 42 between a first end 54 of the housing 42 and the first portion 46 of the movable assembly 44.
  • a second portion 56 of the movable assembly 44 located near a second end 58 of the movable assembly 44, similarly has an outer diameter generally complementary to the inner diameter of an adjacent portion of the housing 42.
  • An additional o-ring or sealing mechanism 60 extends between the second portion 56 of the movable assembly 44 and the housing 42 to prevent a flow of fluid there between. Accordingly, a second chamber 62 is defined within the housing 42 between a second, opposite end 64 of the housing 42 and the second portion 56 of the movable assembly 44.
  • a third chamber 66 is formed generally within the housing 42 between the first portion 46 and the second portion 46 of the movable assembly 44.
  • the third chamber 66 may be formed by varying an outer diameter of the movable assembly 44 between the first and second portions 46, 56 and/or by varying an inner diameter of the housing 42 between the first and second portions 46, 56.
  • the movable assembly 44 is a piston and the first and second portions 46, 56 are integrally formed therein.
  • the movable assembly 44 includes a rolling diaphragm 70 coupled to a piston 68.
  • the third chamber 66 is defined between seal 72 of the diaphragm 70 and the upper surface of the piston 68.
  • a plurality of ports couple to the housing at various locations.
  • a first port 74 is disposed adjacent a first end 54 of the housing 42.
  • the first port 74 fluidly couples the first chamber 52 to the deoxygenation system 14.
  • a second port 76 disposed adjacent the second end 64 of the housing 42 is in fluid communication with ambient air, such as exterior to the energy conversion device 12, and in some embodiments to the vehicle.
  • a third port 78 is arranged in fluid communication with the third chamber 66 and is associated with the fuel pump 20.
  • the movable assembly 44 is configured to move within the housing 42 in response to the pressure generated by the fluids communicated to each of the chambers 52, 62, 66 via ports 74, 76, 78.
  • a first pressure, indicated by arrow P1 is applied by a fluid within the first chamber 56 to the first end 48 of the movable assembly 44
  • a second pressure, indicated by arrow P2 is applied by the ambient air to the second portion 56 of the movable assembly 44
  • a third pressure, indicated by arrow P3 is applied by the exhaust from the fuel pump 20 within the third chamber 66 to a portion of the movable assembly 44 between the first portion 46 and the second portion 56.
  • a biasing mechanism 80 such as a coil spring for example, couples the second end of the movable assembly 44 to an adjacent surface 64 of the housing 42.
  • the biasing force of the biasing mechanism 80 is configured to bias the movable assembly 44 towards a first position, such as shown in FIG. 3 for example.
  • the fluid communicated to the interior of the housing 42 through each of the plurality of ports 74, 76, 78 is dependent on a mode of operation of the vehicle. For example, when an aircraft is grounded and the energy conversion device 12 is non-operational, or is operating in a reduced mode, the pressure P2 generated by the ambient air is greater than the combination of the pressure P3 of the fuel pump 20 and the pressure P1 of the fluid within the first chamber 52. As a result, the biasing mechanism 80 biases the movable assembly 44 to the first position.
  • the pressure P2 generated by operation of the fuel pump 20 is greater than the pressure P3 of the ambient air.
  • pressure P2 overcomes the biasing force of the biasing mechanism 80, causing the movable assembly 44 to transition within the housing 42 towards a second position, shown in FIG. 4 .
  • a vacuum is created within the first chamber 52.
  • This vacuum is applied via port 74 to the deoxygenator system 14 causing the first chamber 52 to fill with oxygen evacuated from the fuel within the deoxygenator system 14.
  • the first chamber 52 defined between the housing 42 and the first portion 46 may be sized to retain all of the oxygen removed from the fuel for the entire duration of the flight.
  • a fluid flow path 82 fluidly couples the first chamber 52 and the second chamber 62.
  • a valve 84 is disposed within the fluid flow path 82 and is operable to selectively expel the evacuated oxygen from the first chamber 52.
  • the valve 84 includes a sealing member 86 biased into a first position to block a flow through the flow path. When the pressure within the first chamber 52 exceeds a threshold, the pressure will oppose the biasing force of the biasing member 88 of the valve 84, causing the sealing member 86 to move to a second position. In the second position, oxygen is able to flow through fluid flow path 82.
  • valve 84 may be selectively opened, such as via a solenoid for example, to allow oxygen to be removed from the first chamber 52 on demand. In an embodiment, the valve 84 is operated during the descent and/or landing of the aircraft.
  • the oxygen within the first chamber 52 may be configured to pass through the fluid flow path 82 and valve 84 into the second chamber 62 when the aircraft is on the ground.
  • the increase in ambient air pressure within the second chamber 62 will cause the biasing mechanism 80 to bias the movable assembly 44 towards the first position.
  • the oxygen within is forced to vent from the first chamber 52 to the second chamber 62.
  • the vacuum assembly illustrated and described herein has a reduced size and weight compared to conventional vacuum systems.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Degasification And Air Bubble Elimination (AREA)

Claims (12)

  1. Ensemble à vide (40) destiné à être utilisé dans un système de carburant d'un aéronef, l'ensemble à vide comprenant :
    un boîtier (42) ;
    un ensemble mobile (44) positionné à l'intérieur du boîtier (42), l'ensemble mobile (44) comportant une première partie (46) et une seconde partie (56), une première chambre (52) étant formée entre le boîtier (42) et la première partie (46), la première chambre étant reliée à un premier orifice de fluide (74) et conçue pour recevoir un premier fluide, une deuxième chambre (62) étant formée entre le boîtier (42) et la seconde partie (56), la deuxième chambre étant reliée à un deuxième orifice de fluide (76) et conçue pour recevoir un deuxième fluide, et une troisième chambre (66) étant formée entre le boîtier (42) et une partie de l'ensemble mobile (44) entre la première partie (46) et la seconde partie (56), la troisième chambre étant reliée à un troisième orifice de fluide (78) et conçue pour recevoir un troisième fluide, dans lequel l'ensemble mobile (44) est conçu pour se déplacer à l'intérieur du boîtier (42) en réponse à la pression générée par lesdits fluides communiquées à chacune desdites chambres (52, 62, 66) par l'intermédiaire desdits orifices (74, 76, 78) ; et
    un mécanisme de sollicitation (80) couplant l'ensemble mobile (44) au boîtier (42), dans lequel l'ensemble mobile (44) est mobile entre une première position et une seconde position à l'intérieur du boîtier (42) par la pression générée par le fluide communiquée à la troisième chambre (66) étant supérieure à la pression générée par le fluide communiquée à la deuxième chambre (62), et surmontant la force de sollicitation du mécanisme de sollicitation (80) en conséquence, pour créer une zone de basse pression entre le boîtier (42) et une première partie (46) de l'ensemble mobile (44) ;
    caractérisé par l'ensemble mobile comprenant en outre
    un trajet d'écoulement de fluide (82) couplant fluidiquement la première chambre (52) et la deuxième chambre (62) ; et
    une soupape disposée à l'intérieur du trajet d'écoulement de fluide (82) et pouvant être actionnée pour expulser sélectivement le premier fluide de la première chambre (52) dans la deuxième chambre (62).
  2. Ensemble à vide selon la revendication 1, dans lequel l'ensemble mobile (44) est mobile en réponse à une ou plusieurs pressions appliquées à l'ensemble mobile (44) par une ou plusieurs sources externes au boîtier (42).
  3. Ensemble à vide selon une quelconque revendication précédente, dans lequel l'ensemble mobile (44) comporte un piston (68).
  4. Ensemble à vide selon une quelconque revendication précédente, dans lequel l'ensemble mobile (44) comporte un diaphragme roulant (70).
  5. Système de carburant (10) comprenant :
    un système de désoxygénation (14) ;
    une pompe à carburant (20) pour fournir du carburant au système de désoxygénation (14) ; et
    un ensemble à vide selon la revendication 1 couplé de manière fonctionnelle au système de désoxygénation (14) pour éliminer sélectivement l'oxygène du carburant à l'intérieur du système de désoxygénation (14), l'ensemble à vide pouvant être actionné automatiquement en réponse à une ou plusieurs pressions externes à l'ensemble à vide.
  6. Système de carburant selon la revendication 5, dans lequel la zone de basse pression est créée, lors de l'utilisation, à l'intérieur de la première chambre (52).
  7. Système de carburant selon la revendication 5, dans lequel la deuxième chambre (62) est conçue pour être couplée fluidiquement à un air ambiant, et la troisième chambre (66) est en communication fluidique avec la pompe à carburant.
  8. Système de carburant selon la revendication 7, dans lequel l'ensemble mobile (44) est conçu pour se déplacer de la première position à la seconde position lorsqu'une pression générée par le fonctionnement de la pompe dépasse une pression de l'air ambiant.
  9. Système de carburant selon la revendication 7, dans lequel l'ensemble mobile (44) est conçu pour se déplacer de la première position à la seconde position lorsqu'une pression générée par le fonctionnement de la pompe dépasse la force de sollicitation du mécanisme de sollicitation (80).
  10. Système de carburant selon la revendication 5, dans lequel le trajet d'écoulement de fluide est conçu pour libérer l'oxygène de la zone de basse pression.
  11. Système de carburant selon la revendication 10, dans lequel la soupape est conçue pour commander sélectivement la libération d'oxygène de la première chambre (52).
  12. Système de carburant selon la revendication 5, dans lequel le système de carburant est conçu pour être associé à un moteur d'un aéronef.
EP18189736.4A 2017-08-22 2018-08-20 Système de vide pour système de dégazage de carburant Active EP3446983B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US15/683,512 US10118109B1 (en) 2017-08-22 2017-08-22 Vacuum system for fuel degassing system

Publications (2)

Publication Number Publication Date
EP3446983A1 EP3446983A1 (fr) 2019-02-27
EP3446983B1 true EP3446983B1 (fr) 2021-08-04

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ID=63404991

Family Applications (1)

Application Number Title Priority Date Filing Date
EP18189736.4A Active EP3446983B1 (fr) 2017-08-22 2018-08-20 Système de vide pour système de dégazage de carburant

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US (1) US10118109B1 (fr)
EP (1) EP3446983B1 (fr)

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Publication number Priority date Publication date Assignee Title
US11000784B2 (en) 2017-08-22 2021-05-11 Hamilton Sunstrand Corporation Vacuum system for fuel degassing
US10556193B2 (en) 2017-09-15 2020-02-11 Hamilton Sundstrand Corporation Integrated O2RU system
US11491421B2 (en) 2018-01-22 2022-11-08 Hamilton Sundstrand Corporation Valve controlled vacuum system
GB2580983B (en) 2019-02-04 2023-10-04 Agilent Technologies Inc Combined Degassing and Circulation of Liquid

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EP3446983A1 (fr) 2019-02-27
US10118109B1 (en) 2018-11-06

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